A FAN DRIVE GEAR SYSTEM FOR DRIVING A FAN IN A GAS TURBINE ENGINE HAVING A HIGH BYPASS RATIO
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United States of America Patent
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Aug 20, 2015
app pub date -
May 6, 2015
filing date -
Sep 27, 2012
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Abstract
A gas turbine engine includes a fan section that includes a fan rotatable about an axis of rotation of the gas turbine engine. A speed reduction device is connected to the fan. The speed reduction device includes a star drive gear system with a star gear ratio of at least 1.5. A bypass ratio is greater than about 11.0.
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